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Characteristics of dual-combustion ramjet

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Thermophysics and Aeromechanics Aims and scope

Abstract

The authors discuss a possibility to use a diverging dual-combustion chamber as applied to high-supersonic boost ramjets operating at flight Mach numbers up to Mf = 8–10. Due to diverging, this chamber allows beginning the ramjet operation from flight Mach numbers Mf ini = 2–3. The diverging combustion chamber is characterized by a ratio of its exit cross-sectional area relative to the cross-sectional area of air-intake throat. This expansion area ratio is determined at Mf = Mf ini, but it should be the same at all flight Mach numbers Mf ⇒ Mf ini, and depends on two factors: the location of a normal shock in the air-intake throat and the condition of reaching the critical velocity at the chamber exit. The dual-combustion chamber provides heat supply in its alone channel first to the subsonic flow and then, along with acceleration of the flying vehicle, to the supersonic flow, which is bound with a decrease in relative heating of working gas. Calculations of characteristics of an exemplified dual-combustion ramjet considered with a twodimensional air-intake were performed in the range of Mf = 3–7.

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Authors and Affiliations

  1. Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia

    Yu. P. Gounko & V. V. Shumskiy

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  1. Yu. P. Gounko
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  2. V. V. Shumskiy
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Correspondence to Yu. P. Gounko.

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Gounko, Y.P., Shumskiy, V.V. Characteristics of dual-combustion ramjet. Thermophys. Aeromech. 21, 499–508 (2014). https://doi.org/10.1134/S0869864314040106

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  • DOI: https://doi.org/10.1134/S0869864314040106

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